Simultaneous experimental verification of indirect thrust measurement method based on Hall-effect thruster and plasma plume

In this work, the experimental verification of the indirect thrust measurement method based on the plume of a low power Hall-effect thruster and its effect on the thruster is investigated. The Hall-effect thruster with per-manent magnets was exhibited and the performance parameters and the plume parameters were introduced, and the thrust of the thruster was measured simultaneously using both direct and indirect measurement methods, which validate the effect due to thruster and the measurement devices. The experimental verification of the thrust amendment values was proposed considering the ion flux collection, the neutral atoms, and the additional momentum due to ion reflecting, and the corresponding amended thrust results were exhibited separately which show the contribution of each factor, and the modification method could provide reliable results for indirect thrust measurement.